NASA TECHNICAL TRANSLATION
NASA TT P-15,037
EXPERIMENTAL AEROGENERATOR
TYPE B.E.S.T.. — ROMANI
DESCRIPTION, ASSEMBLY, TEST PROGRAM
(»aSa-1!T-P- 15037) EXPSfilMENTlL
; AEfiOGEKEBaiOE fYPE BEST - EObIhI
DESCEIPTION, ASSEHBIY, TEST FEOgLh
(Scientxfxc Translation Seririce)£y 5^p hc
''" CSCi 10A
G3/03
N73-29004\
Unclas
11^141 J
Translation of: "Aerogenerateur Experimental
Type B.E.S.T, - Romani Description - Montage
Programme d'essai," Service Des' Etudes Et
Recherches Hydrauliques , Division _Energle
Du Vent, 20, Rue Hamelln, Paris, Electricite
De France, May 1958, pages 5^.
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
WASHINGTON, D.C*; 20546 AUGUST 1973
NATIONAL TECHNICAL
INFORMATION SERVICE
US Dapflrtnent of Comm^fce
SprmgMeld, VA, 22151
NOTICE
THIS DOCUMENT HAS BEEN REPRODUCED FROM
THE BEST COPY FURNISHED US BY THE SPONSORING
AGENCY, ALTHOUGH IT IS RECOGNIZED THAT CER-
TAIN PORTIONS ARE ILLEGIBLE, IT IS BEING RE-
LEASED IN THE INTEREST OF MAKING AVAILABLE
AS MUCH INFORMATION AS POSSIBLE.
STANDARD TITLE PAGE
NASA TT F- 15, 03 7
3. Govarnmanl Ace*i>len No.
4. Titl« ond SublitU
EXPERIMENTAL AEEOGENERATOR TYPE B.E.S.T.
EOMANI DISCRIPTION, ASSEMBLY, TEST PROGRAM
7. Aulhor(i)
9, Petloiming Orgoniiotion Mama and Addrct*
SCITRAN
j^ox 5456
J^^xiLh Barhara, CA iHQB —
12, Sponioring Agsncy Noma arid Add'esi
National Aeronautics and Space Admlnlstraclon |-
Washington, D.C. 20546
3. R<cipi«nl'i Catalog Ng.
5, Raporl Oal«
August 1973
6, Performing Orponliafion Ccd«
8. Parfo'ming Organiioliart Repon No.
10. Work Unit No.
11. Conlrocr or Gronf No,
NASw-2483
13. Typo of Rapoft oni Peftsd Covered
Translation
14. Sponeortng Agency Cede
15. Supplementary Notts
Translation of: Aerogenerateur Experimental Type B.E.S.T. - Romani
Description - Montage Programme d'essai
Source: Se'tvice Des Etudes Et Recherches Hydrauligues, Division
Energie Du Vent, 20, Rtie Hamelin, Paris, Electricite
De France, May 195 8, pages 54.
\6, Abitrocl
A propeller-driven electrical wind generating machine with a
:
30 meter diameter propeller is described. The 160 ton machine.
with a power rating of 640 kW, was built at Nogent-Le-Roi,
France in 195 8. '
1
1
17. Key Wordi {Selected by Autiior(»>}
18. Distribution Stotemont
Unclassified - Unlimited
M. Security Clatiif. (of thU report^
20, Socurlty Claiiif. (of ihii pogo)
31* No. of Page*
33. Pric"*
Unclassified
. _,. —
Unclassified
49
-—
TABLE OP CONTENTS
I
Location and Installation
(Pig.
1)
II
Description of the study static
on
1
and the aerogenerator
(Fig,
2)
A)
Infrastructure
B)
Tlltable part
a)
Pylon tripod
(Fig.
3)
b)
Moveable pivot
with fairing
(Fig,
^)
c)
Nacelle
(Fig.
5)
d)
Generator
e)
Eolian propeller
(Pig.
6)
f)
Transmission
(Fig.
7)
g)
Rate and)
power limit ers
(Fig.
8)
h)
Orientation
1)
Weight breakdown
c)
Ele
ictrical installation
(Fig.
9)
III
Installation
IV
Preparation for operation
V
Me J
isurements
A) Purpose of the test - Measurement quantities
B) Material to be used
C) Test duration
VI Selected photographs
VII Remarks
11
EXPERIMENTAL AEROGENERATOR '
TYPE B.E.S.T. — ROMANI
DESCRIPTION, ASSEMBLY, TEST PROGRAM «
I. LOCATION AND INSTALLATION.
■The wind energy study station Includes an ^elolian propellor| / 2* *
aerogenerator having three blades and a diameter of 30.19 meters.
The test facility includes about 2 1/2 hectares. It is located
2 krn| South wejst of Nogent-Le-Rol (Eure et Loir). It is situated
on Highway No. 1^8 from Courville (Figure 1).
Even though the area does not have particularly strong or
frequent winds, it was selected because the winds are very
regular on a scale of one minute. Also there is a large plateau
'which surround^] the station. There is an extensive plateau region
in the primary wind direction as well.
In this way, there are no houses, trees or substantial
undulations. The station is not located close to the ocean.
Such conditions would lead to regular performances of the device
when meteorological conditions change.
The site is not located in the area around Paris. Thus the
experimenters will not be subjected to various pressures.
French Electrical Corporation Research and Study Directorate
Hydraulic Research and Study Service. Wind Energy Division,
20 Rue Hameim, Paris l6. May 1958.
Numbers in the margin indicate pagination of original
foreign text.
Light pylons have been erected around the apparatus, one of which
is 60 meters long. They are made as transparent as possible to
the wind. They support the control Instruments for directional
control and must withstand the wind velocity.
II. DESCRIPTION OP THE 'S TUDY STATION MP THE .AEROGE NE RAT0R. |
The device is shown in Figure 3. It was constructed under
the direction of the research and study department of the French
Electrical Corporation. Plans were used which were prepared by
the technicians from the Scientific and Technical Study Bureau,
12 Rue Leonlda^, Paris Ih^ .\ This agency is directed by Mr. B.
Romani, engineering consultant.
A. Infrastructure .|
The infrastructure consists of a platform with assembly
terrace, a few meters above the ground. It is star-shaped and
two branches are of a light construction so that they can be
easily moved (extendable tubes). The third member consists of a
small building which houses the transformation station, the
command room and measurement room, the building containing the
batteries, the room for measuring the load and the excitation of
the alternater as well as a small office. A hangep which serves
as a storage area Is also included. The foundations of the
aerogenerator include three concrete substructures located at
the corners of an equilateral t rian gle ,of approximately 2 6 metersl
side length. (Each of them rests onj solid earth plane limonln
to a depth of approximately 1 meter).
The symmetric substructures B and C have a volume of about
70 m3 each. At zero level they support the two feet of the
pylon about which the tilting operation takes place. The sub-
structure A has a volume of about "5)0 m3 and supports the foot
which Is displaced during the balancing operatloHj, and uses a
mechanical screw device. /3
Two additional concrete substructures (called North and South
substructure) have a volume of about 50 m3 and support members
In which the winches of the asynchronous motors are located. These
drive the traction cables and the holding cables for the aerogener-
ator during the tilting operation., (The operational command is
done by means of an intercom system from a building located to the
East in the vertical plane passing through the hinges B and C).
The North substructure is also used to support the portico on
which the tilted aerogenerator rests.
The connection with the main net is made through a 15 kilo-
volt line 12 kilometers long, approximately. Figure 1 shows
the path of this line. Also there is a transformer with ample
capacity (3 MVJA.) which is located at Malntenon (Eure et Loir).
It makes a connection between this 15 kV line and the 63 kV
Elancourt-Bulsant line.
B^;]Tiltable part
a) Pylon tripod
The pylon is shown in Figure 3 and was built at Montreau
(Sejine et Marne ) by the company (*).
The primary pylon structure consists of a triangle system
in space, made up of four Juxtaposed .tetrahedri| (15 bars, 17
nodes). One of the horisontal surfaces of the central tetra-
'hedron makes|up the upper pylon platform at a level of 15 meters
Translator's note: Words illegible in foreign text.
The corner opposite this side Is the 8.5 meter level. The socket
node center of this member supports the pivot. The other 3 tetra-
he dra'are ] identical and each have a common side with the three
lateral sides of the preceding tetrahedron . | The facing corners
of these sides are at zero level. The level points of the nodes
make up the foot of the pylon.
For various reasons, especially in order to sav e t ime, j
the required steel was taken from the inventory of the construction
firm . ■ I^ he pylon tripod weighs 102 tons (tiltable part only).
b) Moveable pivot with fairing.
The pivot shown in Figure 1 is a tube made up of two opposed
cones with a total length of 22 meters. It is made of steel
sheet metal and welded to a depth of l8 mm.
The central part of it consists of a cylindrical rolling
surface part made up of heavy steel. The rollers;, mounted! in
pairs along six rudder bars, press-. against_] the rolling surface.
The vertical axes of the rudder bars are connected with the pylon.
An external fairing made up of thin steel sheet m.etal con-
tains the access ladder to the nacelle. It is there in order
to reduce the Interaction between the wake and the eolian
propeller located downstream.
c) Nacelle
The nacelle. Figure '5|, made of thin riveted steel sheet
metal Is installed within the interior of the upper extremity
of the pivot. It supports the upstream fairing and the brake
fairing.
The nacelle Is extended in the upstream direction by the brake
and by means of a forged steel member. This is done by means /4_
of a large dimension ball bearing which supports the eollan
propellor. It is surrounded by two foot bridges located above
one another. One of them contains the hydraulic control devices.
d) Generator
The («) generator, 3,000 Volts, 1000 r'p|ra, 64o k¥, 800 kV, Is
Installed in the frames of the nacelle. This generator has
separate excitation (on the ground) and is supplied by a power-
ful squirrel cage damper. It is used to start the asynchronous
motor.
The flexible ground connection cables (3-phase excitation,
measurement cables and probe cables) are run vertically within
the interior of the pivot and can sustain a torsion of somewhat
more than one rotation.
e) Eollan propellor
Each of the three blades (Figure 6) is made of unoxidizable
light alloy (AZ 4 called T 33, made by (*) atLelHavre) and is
made with a riveted construction. The roots of the blades are
made of riveted steel and are bolted. There are two flanges
of steel. These parts make up the hub. The dihedral is 8°.
The hub is extended by means of an upstream cylinder connected,
with the brake. Also there is an upstream cone which engages the
Translator's note: Illegible In foreign text.
coupling. These auxiliary structures are made of steel. The
hub has a fairing between the blades. Also there are removable
fairings made of T 35. There is a turning device for manual
turning of this propeller . Under normal conditions, it turns
at 17 rpm. It was constructed at Bordeaux (Glronde) and part
of it was constructed at Valencionnes (Nord). The fabrication
was performed at the Industrial Transport Material Company,
f) Transmission
A device used on electrical locomotives has been extended.
The eollan propellor drives a first planetary gear train, having
the following characteristics: interior tooth fixed crown (Model
11) with 109 teeth, three 46-_t_qQth sat ellites and a IT-tooth plane^l
tary gear.
An intermediate shaft having an exterior diameter of 260 mm
revolves at 350 rpm and connects the first gear to the second
gear train. It passes through the center of the journal support-
ing the propellor. Couplings with "boat" notches allow a cer-
tain misalignment. These mlsalighments are unavoidable because
of the' large -S'i'Z fr. -.of •the structure.
The following characteristics apply to the second gear train:
crown driven by an intermediate shaft (module 8, 77 teeth)i one 25i-l
tooth satellite connected with the clutch by means of a shaft
which drives the satellite^. These pass th ro ugh thej ci^ossed shaft of]
the generator. Twenty seven^ooth planetary gear^sT]
The teeth of the two trains are right angle ones. The /5
fixed part of the clutch is balanced and strain gauge rods
make it possible to measure the reaction moment on the nacelle.
The transmission, the pivot and the nacelle were built by the
Mediterranean Forgery and Steelworks (LeJ Havre Division - Maritime
Seine Division.
Figure 7 shows a diagram of lubrication for the two gear
trains.
g) Rate and power limit ers
If the blades of an eolian propeller have a fixed adjust-
ment, a very effective control is obtained automatically and
without cost by connecting the generator with an alternating
current network.
In effect, the incident wind is the geometric sum of
a relative component due to rotation and the natural wind.
When the rate of rotation is constant » the wind increases and
the velocity triangle is deformed. Due to the effect similar to
the "velocity loss" over an aircraft wing, the power produced by
the propeller through the generator can decrease after passing
through a maximum. It begins to increase again slowly only for
considerable wind velocities.
On the other hand, the propellor will race when the network
fails. The BEST-Romani aerogenerator has four methods of
counteracting this situatlon,|
The most classical solution is a disc brake with hydraulic
controls, with which it is possible to apply a resisting moment
of 40,000 m kG to the propellor. The components selected have
an increased effectiveness as temperature increases, in^ contrast
to what is used in automobiles. An electrical brake can be ob-
tained by substituting an electrical resistance for the failed
network. This distance consists of a l'6|0 meter long, three phase
suspended line which is cooled by the wind and made of three
lengths of flat TOPHET] ribbon arranged in the shape of a star.
This resistance can dissipate up to 1100 kW,
Slowing down devices, called "spoilers", are installed on
each blade. Under normal operating conditions, they are re-
tracted into the leading edge. When they are extended, under
the influence of centrifugal force, they can instantaneously
destroy the aerodynamic properties of the profiles used.
Finally, if none of these procedures can slow down the
propellor, it may be possible to change the orientation of the
entire aerogenerator installation.
Figure 8 shows the hydraulic command units.
h) Orientation
Above the upper pylon platform, there will be an electrical
command gear mechanism with which it is possible to change the
orientation of the pivot. This command itself can be servo- /6_
controlled by means of an air sleeve outside of the wake of the
eolian propellor,
i) Weight breakdown of the tiltable part
Pylon 102 tons
Pivot with fairing 25 tons
Nacelle ,, 10 tons
Generator .,,. 6 tons
Eolian propellor and
rotating fairings • . . . . 8 tons
Transmission ...... . . 9 tons
Total 160 tons
C, Electrical inst allation|
It Is shown In Figure 9. The selector makes It possible
to operate in the safety mode using the local 15 kilovolt system.
It is usually open.
Very detailed instructions for operating the installation
at Nogent-Le-Roi were worked out. with various interested services
of the French Electrical Corporation, This was done so as to
avoid any accidents involved with supplying the energy generated
by the wind to the "6J3 kilovolt general network,
IIIj INSTALLATION
The Installation work for the aerogenerator was started in
1955, The buildings and these foundation substructures were
built in 1956 as well as part of the electrical installation.
These were built by the Anthony (Seine) French Electrical
Society.
The installation of the tiltable part could only be started
in the year 1957. This was because of labor problems of the
installation and worker's union of VillelJuif (Seine),
Some work remains to be done (balancing of the propeller,
installation of the upstream and downstream fairings, installation
of the orientation mechanism, moun t in gj^^? P o iTe rsr,~^pa i n t ing" o/j
the entire device) which will make it necessary to lower the
tiltable part in the foreseeable future.
We believe that the entire installation will take up I8
months. During this period, the device will have operated.:, and
most of the runnlng^n work and the preparation work will have
/ 7
been completed,
iV.] PREPARATION FOR OPERATION
At Nogent-Le-Rol, the alternator was first connected with
the net on March 15, 1958, It operated as a synchronous compen-
sator*.
The uncoupled propeller was set free in the wind on March 19 a
1958, It was operated by a wind having a velocity of about
i,3jO m/sec. When it reached the velocity of about 53 rpm,
corresponding to a wind of 6 m/sec and a free-wheeling peripheral
WR
velocity coefficient (-ir-) on the order of 1^, it was stopped by
the mechanical brake in about 7 seconds.
The alternater-propellor complex first delivered power to
the net on April 2, 1958, On April 11, a power level on the
order of 200 kW was reached for winds which varied between
7 to 11 m/sec approximately. The charge threshhold seemed to be
som.ewhat less than 7 meters/sec. For the time being and up
until the running-|ln work has been completed, we do not want to
exceed these values.
Between zero and 200 kW, there was no abnormal vibration
or pumping to be observed,
V. MEASUREMENTS
A, Purpose of the test - Measurement quantities,
a) Measurement of the performances of the device.
Establish the following curves:
Useful power, wind velocity (free orientation,
(slaved orientation,
(displaced orientation, etc.)
10
b) Analyse the electrical losses and derive the
following curves:
Propeller power coefficient - wind velocity
c) Determine the best excitation setting (Stability,
(Maximum production, etc.)
d) Devise the following exploitation methods:
Permanent coupling or uncoupling because of wind
velocity less than the charge threshhold, re-
quirement for a collector in the pivot, etc,
e) Compare to various braking and slowing down pro-
cedures:
Mechanical braking, electrical braking, aerodynamic
braking, change orientation by 90°,
f) Study the possibilities of simplifying the maintenance:
Pivot fairing.
Orientation,
Slow motion, etc.
g) Verify the calculations of the aerodynamics and the
strength of materials. Provide Information regard-
ing the vibrations observed by measuring the stresses
using wire strain gauges (in the eolian propellor,
in the infrastructure, etc.) or by using differential
micromanometers .
h) Study the wakes.
B, Equipment to be used.|
a) Measurement of the direction and the velocity of the
wind,
1) Air. sleeve containing selsyns and butterfly
spinners
2) Butterfly anemometer (sensitive to E) and
anemometers which measure the theoretical
collectible energy, built by the counter
company at Montrouge (Seine).
11
3) Rough cylinder anemometers (with a response /8
time on the order of 0,2 sec and which
measure V^).
- At the beginning, old model anemometers mounted]
as a wind vein.
- After that, astatic anemometers with two
orthogonal components.
Note: The problem of a reference velocity is very
difficult because of the following factors:
1) Interactions between the aerogenerator and the
anemometers.
2) Because of the Irregular nature of the wind
in space,
3) Because of the non-steady character of the wind,
4) Because of the variable vertical gradient of
its velocity,
5) Because of the orientation motions of the aero-
generator,
6) Because the cube of the velocity enters in the
ratfi-'6f. reduction of the measurements.
If there is only one anemometer, it should be mounted on the
same pivot as the aerogenerator, in order to function well.
However, since this is impossible, it must be installed upstream
by means of a horizontal mass in exactly the axis of the pro-
peller. This means that it is not possible to carry out a
calibration beforehand. This method can only be used if another
device is available which is more accurate which is available
for calibration in free air (an anemometer support has been
planned upstream on the fairing in order to perform such a cali-
bration). ■ According to the recommendation of (*) document
30.001 regarding|low power aerogenerators for the A.P.N.O.R., it
Translator's note: Illegible in foreign text.
12
Is possible to Install two anemometers to the left and right
of the eollan propellor at the level of the axis and at distances
which are equal but not too large. At Nogent-Le-Rol, we use a
120 meter separation. This value is too large for the anemometers
to be supported by the aerogenerator itself. This is why three
pairs of support pylons were deemed necessary, (see Figure 1),
At all times, only one pair was used,
b) Recording and reading of the Instruments
1) A laboratory truck of the study and research
directorate: recording of the transient operating ranges such as
the starting of the alternator in the asynchronous Mpde during the
connection process to the net and during coupling of the pro-
pellor,
, 2) With a simple photographic recorder, recording of
the rotation rate of the propellor (free wheeling — deceleration
at the time of braking, etc.)
3) Using a plate photograph device or an oscilloscope.
Any variable can be used as the abscissa value (for example the
poxver with modulation coupling (*) and with any ordinate value:
study of possible correlations. There is the possibility of
recording the oscilloscope pictures on a movie camera,
4) By means of an ultra-fast camera: it is possible
to take moving pictures of the propellor and to play them back
slowly afterwards,
5) Using two accelerometers in conjunction located
in a horizontal plane, located in the n]acelle. Also a recorder
* Translator's note: Illegible in foreign text,
13
Is used. Detelctlon and measurement of the overloads which
probably exist when starting, /9.
6) By means of a photographic, multitrack
recorder: recording of watt meter readings, volt meter read-
ings, angular separation between the wind and the propeller,
readings of the coupling meter, readings of the rate of rotation,
reading of the reference velocity and recording of the time.
Also, pivot gauges, reference velocity and time can be recorded
as well as pylon gauges, reference velocity and time,
7) Using a recorder| located Inside the hub:
recording the readings of gauges and transducers located in the
blades, with remote controlled starting and synchronization
with the recorder mentioned previously.
Note: A more ambitious program was planned which also included
simultaneous measurements on the three blades using various
numerous transducers| and gauges connected to the multitrack
recorder, which has radio transmission capability. In order to
limit the expenses, this plan was abandoned. It will be possible
to go back to this plan because of the fact that it is possible
to balance the device. Also wires and pipes have been left
inside inaccessible, parts of the blades.
8) At Nogent-Le-Rol there are a certain number
of instruments on the control panel at the control and measure-
ment room. Their readings will simply be read off during a test.
Only this will be done because the readings va|ry slowly (current
intensity, probe temperatures in the (*) of the stator of the
generator, etc, )', alsoj the measurement variables could be
mathematically related to quantities which are already recorded
* Translator's note; Illegible in foreign text.
Ik
(varying mass of air, power factor). Also they are not recorded
because some of them are only required over a certain time inter-
val (oil flow rate). As far as the measurement of the air
volume is concerned, there is a mercury baromete r^ as| well as
dry and wet thermometers,
9) We intend to study the wind at Nogent-le-Roi
using, for example, electronic devices which will make it
possible to make a classification according to frequencies. Also
we will use devices made by the Transdjucer Society for recording
the following curves: wind energy integrated over one minute,
as a function of time. Also we can study the correlation be-
tween wind and rain (pluviograph recorder). Finally we may
make use of the permanent personnel at the installation (during
the day and during the night). We will use them especially if
we are to take readings every hour over a period of several
days.
'C. __Test duration]
The tests have extended over several months. They
are distributed over one year so that we will encounter the
largest number of wind variations. /lO
VI, SELECTED PHOTOGRAPHS
This report also contains a number of photographs .taken
during the preliminary tests, the erection phase and the con-
struction phase, of the aerogenerator at Nogent-Le-Roi. We also
show a photograph of the complete machine.
15
VII. REMARKSl
In order to test the Idea of transforming wind energy into
electrical energy we constructed a preliminary experimental
device. The dimensions of this device may seem enormous con-
sidering the approximately one million and a half kilowatt hours
which it is capable of producing per year, if it were located in
Brittany or at Cotenln at a well selected site^._] We can see that
the wind energy is not very dense.
The origins of this machine were inspired by machines used In
industry or fabrication which are built in large series (automo-
biles, trains, electrical pylon supports, servo mechanisms) .]}■,:?
We were more concerned with techniques, for providing safety iratherj
than for reducing costs (aeronautics, marine technology, bridge
construction). We were hampered by the fact that there was no
precedent to our work. Our project will considerably simplify
future work. It may become possible to omit elements which we
had to include and which would have been impossible to add
afterwards (clutch, multiplier, brakes, hydraulic controls,
orientation, balancing, intermediate electrical transformation
to low voltages, etc.).
The device at Nogent-Le-Roi is therefore a prototype. The
large aerogenerators which may be built later on, on a small scale; andj
provided the cost is not too large, may be quite different.
However, their slllouette will be the same as will be their
relative dimensions (*),
Many words illegible in foreign text,
16
Figure 1.
Study station for wind energy
Nogent-Le-fRoi
(Eur 8 et Loir)
Location and installation
17
.!, ; I aero gen e r a t o r.
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50.000
NOT REPROpUClBLE
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A
A-B-C: Substructure and feet of the pylon
of the aerogenerator ,
Winches
Aerogenerator
Control and irieasurement building.
Mounting platform
Command unit for winches
Resistance electrical line
Hangar- storeroom
Beginning point of 15,000 V suspended ^.<^oi
line •
Supporting 60 m pylon which
supports the directional air
channel
l_2-3-4-5-6-8-9: 33 m pylon
which support the anemomel
D-E
F
G
H
I
J
K
L
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B
n
D
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,Scalei
innn
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: rm
upstream fairing
wind dlrectionl
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Figure 2. Entire aerogenerator complex,
20
17, S^5 /»
Figure 3. Pylon tripod
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Figure 5.
Longitudinal ■ cross section of the nacelle
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2nd gear and alternator bearings
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p-t^
Thermal probe
-1st and 2nd gear case [
Alternator bearing's"
Overfill control
•Control flow rate
Dispatch
Level contact
Magnetic stopper
Figure 7. Lubrication circuits
26
,Blade locking, devlcej
Figure 8. Hydraulic controls
27
Clutch
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TT3 3TS"
■.-
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Figure 8 (Cont'd)
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A.
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1 engagement j'ackj,
"disengaged p " "
position^
A:
Filter
G:
Accumulator
B;
Pump
H:
Manometer
C;
Electrical motor
J:
Manometer contact
D:
Hand pump
K:
Choke
E;
By-pass
L:
Electrical valve
P:
Anti-return Valve
Y:
Magnetic stopper
V:
Hydraulic valve
28
Figure 8 (Cont'd)
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29
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^Figure 9. Electrll^al
'■'.'j installation]'. ■
•fi^rf diagram. :'^;"^^ ■' "' ' ••: r-
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■Figure ij.
Figure's r-2".| Before constructing the 30.19 mete rs aero generator
(diameter of the eolian propeller) numerous laerodynamicT studies)
were carried out, including investigations at the Eiffel wind~'
tunnel, the Chalals Meudon wind tunnel and the St. Cyr School wind
tunnel. Investigations in natural wind were carried out at
Poitiers.
[ ■ - Pigures^3r^rrd~2"show the 1/-8 scale model and theT7?"0l
Jmodel of the aerogenerator. i
31
Figure 2\.
32
Figure 3. The same tests were done to determine the strength
of the materials. ■(Deformation under a Idad^ farigiie Because
of alternating loads, measurement of vibration periods, etc.))
Various elements of the eollan propeller and elements of the
transmission system were tested. This was done at the public
works and building laboratories, at the bridge laboratory
and at the facilities of the contractor.A^ The figure shows a
destruction test of a full-sized blade at the aeronautical
facility at Toulouse.
33
-tr
Figure 4. In the figure one can distinguish the concrete structure. It shows the
support around which the tilting pylon foot will turn. The pylon rests on the
ground. Suspended in mid-air, we can observe the socket which will support the
lower part of the moveable pivot.
Figure 5. View of the pylon during construction.
■^-^•v
•T-mm^tj
Figure 6. The pylon is shown during the tilting operation and
Is being tilted around two of Its legs. The cables which
connect it with the North arm are still under tension. After the
structure has reached equilibrium, the connection with the
moveable South foot will be set into operation in order to reduce
the descent v!§locity.
36
Figure 7. This photograph of the left side shows the upper part of the tilting pylon
which rests on a portico and which will contain the pivot. On the right side, we can
observe the windows of the electrical and transformation station. Through the win-
dows we can observe the control and measurement room.
—J
Ul)
oo
; Figure 8 -
Figures 8-9. The blade caisson is made of unoxldizable alloy. It is shown during
assembly onto the steel hub. The lower member rests on a construction supported by
the mounting platform. Electrical cables are shown which measure the stresses
in the blades.
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Figure 9
Figure 10. Above the hub of the eollan propeller, we observe the
following from bottom to top; the lantern wheel which is acti-
vated by a gear pinion which makes it possible to rotate the
propeller by hand, 3lhe Journal, then the brake and then the
nacelle.
40
I Cir g^j ' ^ ii'^ ^"""^^'fi< ' ^ 'n'iT Y
ll u , t. * ' k? V* ^4 ' t ^
ft
, ,.„; :;'V; ■'>^*a<f<
A
^^^mxlL^n^
*^'.^XIir'':cn'Trr i f„^l'!v?^^"
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Figure 11. The first gear wheel is placed above the propeller hub, which had
been raised beforehand.
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Figure 12. At the same time the trailing edges of the blade and the leading
edges containing "spoilers" are Installed.
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i ^
V
^ til' fe
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^
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:|
Figure 13. Once the nacelle Is covered within the pivot, the 640 kW generator is
brought Into final position. The second gear train is already installed in the
upper support.
Figure 14. The clutch Is lifted onto its tower.
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Figure 15. A coupling of the model utilized for electrical locomotives connects the
propeller hub to the first gear train. Only couples can be transmitted.
a\
■■■ ■.. ts.
Figure 16. The aerogenerator Is In the process of being raised. The operation lasts
55 minutes in all.
W inl^ > ..,-'-^''"'**'
■'*'^'^**^*^Atei«^^i
kJi£:
Figure 17. The moveable foot is being attached to the concrete substructure.
Figure l8. The aerogenerator has been erected. The final
fairings must be Installed and the nacelle is surrounded by
protective covering members.
Translated for National Aeronautics and Space Administration under
contract No. WASw 2483, by SCITRAN, P. 0. Bos 5456, Santa Barbara,
California, 93108.
48
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